全文获取类型
收费全文 | 235篇 |
免费 | 70篇 |
国内免费 | 37篇 |
专业分类
航空 | 105篇 |
航天技术 | 55篇 |
综合类 | 1篇 |
航天 | 181篇 |
出版年
2024年 | 3篇 |
2023年 | 8篇 |
2022年 | 22篇 |
2021年 | 29篇 |
2020年 | 22篇 |
2019年 | 16篇 |
2018年 | 17篇 |
2017年 | 7篇 |
2016年 | 10篇 |
2015年 | 16篇 |
2014年 | 25篇 |
2013年 | 25篇 |
2012年 | 14篇 |
2011年 | 19篇 |
2010年 | 9篇 |
2009年 | 4篇 |
2008年 | 5篇 |
2007年 | 15篇 |
2006年 | 11篇 |
2005年 | 7篇 |
2004年 | 8篇 |
2003年 | 8篇 |
2002年 | 2篇 |
2001年 | 4篇 |
2000年 | 4篇 |
1999年 | 7篇 |
1998年 | 5篇 |
1997年 | 8篇 |
1996年 | 2篇 |
1995年 | 2篇 |
1994年 | 3篇 |
1993年 | 2篇 |
1992年 | 1篇 |
1990年 | 2篇 |
排序方式: 共有342条查询结果,搜索用时 484 毫秒
171.
《中国航空学报》2021,34(6):178-187
The integral shrouded blisk provides better performance with minimum weight, but its semi-open structure presents problems for its production. Manufacturing processes of these components require a removal of about 70%-90% of material from their blanks. Multi-axis electrical discharge machining (EDM) is commonly used for these processes, but its poor efficiency cannot meet the requirements of mass production. Strong flushing assisted high-current discharge is able to improve the machining efficiency. In this paper, this method was applied to manufacture the integral shrouded blisk. An electrode design method was proposed. Taking the largest revolving entity inside the flow channel as the base geometry, this laminated arc-shaped hollow electrode meets the requirements such as high pressure flushing, tool wear compensation, and easy to be made. A 4-axis linkage machining tool path with planetary motion was proposed. Taking an integral guide vane ring as an example, it has been experimentally verified that the time consumption for each channel using this method was reduced to a half of the ordinary EDM method, while the finished surface quality remains same. 相似文献
172.
Sangjong Lee Jieun Jang Hyeok Ryu Kyun Ho Lee 《Advances in Space Research (includes Cospar's Information Bulletin, Space Research Today)》2014
This paper concerns optimal trajectory generation and nonlinear tracking control for stratospheric airship platform of VIA-200. To compensate for the mismatch between the point-mass model of optimal trajectory and the 6-DOF model of the nonlinear tracking problem, a new matching trajectory optimization approach is proposed. The proposed idea reduces the dissimilarity of both problems and reduces the uncertainties in the nonlinear equations of motion for stratospheric airship. In addition, its refined optimal trajectories yield better results under jet stream conditions during flight. The resultant optimal trajectories of VIA-200 are full three-dimensional ascent flight trajectories reflecting the realistic constraints of flight conditions and airship performance with and without a jet stream. Finally, 6-DOF nonlinear equations of motion are derived, including a moving wind field, and the vectorial backstepping approach is applied. The desirable tracking performance is demonstrated that application of the proposed matching optimization method enables the smooth linkage of trajectory optimization to tracking control problems. 相似文献
173.
Xu Huang Ye Yan Yang Zhou 《Advances in Space Research (includes Cospar's Information Bulletin, Space Research Today)》2014
The Lorentz force acting on an electrostatically charged spacecraft as it moves through the planetary magnetic field could be utilized as propellantless electromagnetic propulsion for orbital maneuvering, such as spacecraft formation establishment and formation reconfiguration. By assuming that the Earth’s magnetic field could be modeled as a tilted dipole located at the center of Earth that corotates with Earth, a dynamical model that describes the relative orbital motion of Lorentz spacecraft is developed. Based on the proposed dynamical model, the energy-optimal open-loop trajectories of control inputs, namely, the required specific charges of Lorentz spacecraft, for Lorentz-propelled spacecraft formation establishment or reconfiguration problems with both fixed and free final conditions constraints are derived via Gauss pseudospectral method. The effect of the magnetic dipole tilt angle on the optimal control inputs and the relative transfer trajectories for formation establishment or reconfiguration is also investigated by comparisons with the results derived from a nontilted dipole model. Furthermore, a closed-loop integral sliding mode controller is designed to guarantee the trajectory tracking in the presence of external disturbances and modeling errors. The stability of the closed-loop system is proved by a Lyapunov-based approach. Numerical simulations are presented to verify the validity of the proposed open-loop control methods and demonstrate the performance of the closed-loop controller. Also, the results indicate the dipole tilt angle should be considered when designing control strategies for Lorentz-propelled spacecraft formation establishment or reconfiguration. 相似文献
174.
为实现航天器安全准确地沿最优飞行轨迹再入,对航天器再入飞行过程中任意时刻飞行状态,在满足所有约束条件下,计算航天器所能达到的地面最大着陆区域,以判断该时刻飞行器能否到达预定着陆点。文章采用改进的遗传算法对航天器再入飞行轨迹进行优化,结合再入动态终迹圈计算方法,实现再入动态终迹圈的仿真计算。通过对仿真结果的对比分析,得到再入动态终迹圈及相应再入飞行轨迹的特性,对航天器再入飞行制导及航迹规划具有一定的借鉴意义。 相似文献
175.
176.
177.
178.
从解算弹道的逐点多站最小二乘算法得到的弹道精度出发,给出了一个全测速多站系统的最优布站数学模型,并通过大量试算选定了具有良好收敛性的数值算法.初步的计算表明:对全测速多站系统,其最优布站方案与现有布站方案在弹道精度上有着显著的差别;在最优布站方案下可确保逐点多站最小二乘算法具有良好的数值稳定性,并得到满足精度要求的外测弹道. 相似文献
179.
为了更好解决复杂多约束下的在线轨迹优化问题,研究了一种基于联立求解框架进行轨迹优化的算法。此方法是一种直接法,先利用有限元正交配置法将状态和控制变量同时离散化,然后使用内点算法对离散得到的非线性命题进行求解。从平衡解的精度和计算代价的角度出发,引入了针对内点算法的收敛深度控制策略来改进方法的快速收敛性。最后,以某航天器月面上升段最优入轨任务为算例,验证了算法的精度和快速收敛性。 相似文献
180.
针对火星进入段制导存在的“进入状态偏差”问题进行脱敏轨迹设计研究,以增强制导鲁棒特性,提升末端状态精度。首先分析倾侧角反转逻辑对弱机动能力航天器制导精度的影响,结果表明, 存在倾侧角调整性能约束时,反转逻辑会引起末端状态偏差并使系统对进入状态偏差敏感度上升,当制导采用现有纵向脱敏方法时其影响尤为突出,会导致严重失效问题;然后在解决敏感度传播奇异问题的基础上提出三自由度脱敏设计。其主要思路是轨迹优化中采用三自由度动力学方程,而敏感度罚项仍由纵向敏感度传播方程得出。蒙特卡洛仿真结果表明本文方法对进入状态偏差具有显著增强的鲁棒性能。 相似文献